Pump



Dec. 2, 1924-A 1,517,461

H. A. ROBINSON PUMP Original Filed Aug. 23, 1918 #www Patented Een 2,i924.

narran stares earner aerien.

HUGH A.. ROBINSON, OF KEYPORT, NEW 3ER-SES?, ASSIGNOR TO AEROMARINEPLANE @a MOTOR CO, INC., A GO'RORA'IIGN 'OF NEW YORK.

EUMP.

Application filed August 23, 191.8, Serial No. 251,070 Renewed April 28,1924.

To all ywhom it may cm2-cern.' c

Be it known t-hat I, InIUGr-r A. ROBINSON, a citizen of the UnitedStates, residing at Keyport, in the county of Monmouth and State of NewJersey, have invented certain new and useful Improvements in Pumps, ofwhich the following isa specification, reference being had therein tothe accompanying drawing.

rIhe invention relates to wind-operated pumps of the class ofgasoline-pumps used on aircraft, and the object is to provide a pump ofthis nature characterized by great simplicity, reliability anddurability.

In the accompanying drawings, I have illustrated in Fig. 1 inperspective partly broken away and partly in cross-section, a suitableform of pump embodying an application of my invention. Fig. 2 is acrosssection through. the upper part of Fig. 1, and Fig. 8 is anenlarged sectional detail showing the method of mounting the gears.

4t indicates a suitable bracket by which the pump is attached to anaeroplane, dirigible or other vehicle adapted to travel through the air.The onrushing atmosphere acts upon the hemispherical anemometer cups 5upon the ends of the arms 6 which are mounted upon the shaft 7 whichpasses through the tubular casing 8. Said shaft is enlarged at thebottom and top as indicated at 9-9, leaving asnbstantial clearance 10forming a deep annular reservoir between said shaft 7 and the shell 8,which may be replenished occasionally with grease or tallow from the cup11 secured to the casing in communication with the reservoir. The upperend of this shaft passes through the bottom of the gear casing 12 whichis recessed to receive the hardened steel washer 13 over which issecured the gear 14. upon the end of said shaft 'i'. This gear mesheswith the gear 15 upon the shaft 7 and the casing 12 is formed with thepassagesl-l. The gasoline or oil is drawn into the passage 15 by theaction of the gears from which point it is passed by the gears throughthe outlet 16 to the engine. The pin 17 is preferably passed through thewasher into the plate 12 to prevent the wear of the plate, thus any wearis taken up by the gear which may be renewed.

With this arrangement a constant pu1nping of gasoline is provided whilethe plane is in movement or the engine is in operation,

the back draft from the propeller serving to keep the pump in operationeven though the plane or other vehicle is standing still and thearrangement provided is so simple of construction and few of parts as toinsure against getting out of order.

The aneinoineter motor has a comparatively narrow range of speeds fordiderent speeds of flight, so that the pump is never driven atdestructive speeds on the one hand, or on the other hand ever operatedat so low a speed as to fail to deliver the requisite quantity ofgasoline or oil. Atvthe speeds at which the gear-pump element is drivenby the direct-connected anemometer it is exceptionally durable and doesnot cut out in the presence of gasoline. The pump therefore remainspositive in its action, and it is not subject to leakage. Furtheradvantages are lightness, and the capability of the device of beingplaced in a variety of positions on the plane with equal efficiency ofoperation. The gasoline from the interior of the casing works into thelubricating material in the reservoir 10, dissolving it gradually andcausing it to reach the gears, which are thereby lubricated. In this wayan automatic reservoir diffusion feed is provided, which enables thepump to operate without injury or attention over long flights, and whichas an element of an aviation pump is very simple, compact and light.

Of course it will be understood that various modifications may be madein the construction and arrangement of parts without departing from thespirit of the invention as claimed.

I claim:

1. A pump suitable for supplying gasoline to a moving engine so as atall speeds to supply its needs, comprising a casing with inlet andoutlet ports, intermeshing gears nested in the casing; a spindle for oneof the gears, and an anemometer connected to the spindle to operate thesame whereby the pump will be operated at low speeds of translation ofthev engine but the range of speed at which it is driven will be keptwithin desirable limits notwithstanding high speeds of translation ofthe engine.

2. A pump for supplying gasoline to a moving engine so as at all speedsto supply its needs to the' engine, comprising a casing with inlet andoutlet ports, interineshing gea-rs nested in the casing; a spindle forone oithe gears, an aneznoineter connected to the spindle to operatethesaine whereby the pump will be operated at low Speeds of translationof the engine but the range of speed at which it is driven will be keptwithin desirable limits notwithstanding excessive speeds of translationof the engine, and lubricating ineans around the spindle, there being acommunication between the gasoline passed through the puinp and thelubricant.

3. A pump for supplying gasoline to an aircraft engine, comprising ahorizontal cas ing with inlet and outlet ports, horizontal gears restingon the bottoni of the casing, a vertical spindle for one oit the gearsand an aneinoineter on the spindle to operate the saine whereby thepuinp will be operated at all speeds of the engine but the rangel ofspeed at which it is driven will be kept within desirable limitsnotwithstanding high speeds of motion oi the aircraft.

4L. A pump of the class described comprising zi casing having agear-case part and a tubular part, meshing gear-pump members in saidgear-oase part, a driving shatt in said tubular part connected-to oneoit said gear members, and an aneinoineter wind-inotor for driving saidshaft, there being formed between said shaft and tubular casing part anelongated annular reservoir into which the liquid troni the gear-casepart can pene-- trate to carry lubricant gradually by ditfusion to thegear ineinbers.

In testimony whereof hereunto attix in v signature in the presence oftwo witnesses HUGH Si. ROBINSON.

Titnesses DAvID H. DoUGLAss, THOMAS A. HILL.

